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EPPLER 1230 AIRFOIL (e1230-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 1230 AIRFOIL (e1230-il)
Reynolds number: 100,000
Max Cl/Cd: 35.79 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e1230-il-100000.txt
Download as CSV file: xf-e1230-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 1230 AIRFOIL                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4282   0.09708   0.09277  -0.0490   1.0000   0.1440
  -9.250  -0.4156   0.07834   0.07396  -0.0532   1.0000   0.0914
  -9.000  -0.5341   0.06865   0.06411  -0.0513   1.0000   0.0751
  -8.750  -0.6393   0.06266   0.05747  -0.0425   1.0000   0.0675
  -8.500  -0.6177   0.06173   0.05696  -0.0414   1.0000   0.0695
  -8.250  -0.6407   0.05752   0.05241  -0.0385   0.9982   0.0660
  -8.000  -0.6191   0.05107   0.04546  -0.0430   0.9883   0.0639
  -7.750  -0.5958   0.04493   0.03858  -0.0464   0.9781   0.0625
  -7.500  -0.5642   0.04073   0.03380  -0.0492   0.9678   0.0632
  -7.250  -0.5306   0.03764   0.03009  -0.0516   0.9562   0.0662
  -7.000  -0.4918   0.03486   0.02699  -0.0545   0.9461   0.0697
  -6.750  -0.4527   0.03278   0.02473  -0.0567   0.9346   0.0735
  -6.500  -0.4144   0.03061   0.02229  -0.0587   0.9229   0.0792
  -6.250  -0.3728   0.02904   0.02049  -0.0611   0.9121   0.0881
  -6.000  -0.3256   0.02706   0.01855  -0.0645   0.9043   0.1009
  -5.750  -0.2863   0.02544   0.01707  -0.0665   0.8925   0.1173
  -5.500  -0.2373   0.02391   0.01552  -0.0701   0.8854   0.1432
  -5.250  -0.2029   0.02257   0.01439  -0.0713   0.8708   0.1671
  -5.000  -0.1673   0.02151   0.01334  -0.0724   0.8562   0.1957
  -4.750  -0.1330   0.02032   0.01239  -0.0734   0.8418   0.2296
  -4.500  -0.1023   0.01909   0.01149  -0.0737   0.8271   0.2797
  -4.250  -0.0829   0.01767   0.01082  -0.0720   0.8115   0.3922
  -4.000  -0.0681   0.01760   0.01154  -0.0679   0.7943   0.5647
  -3.750  -0.0449   0.01831   0.01211  -0.0654   0.7773   0.6279
  -3.500  -0.0215   0.01885   0.01246  -0.0630   0.7612   0.6644
  -3.250   0.0031   0.01916   0.01262  -0.0610   0.7462   0.6920
  -3.000   0.0295   0.01937   0.01266  -0.0592   0.7327   0.7166
  -2.750   0.0504   0.01951   0.01270  -0.0568   0.7173   0.7378
  -2.500   0.0733   0.01966   0.01276  -0.0546   0.7031   0.7567
  -2.250   0.0986   0.01980   0.01275  -0.0528   0.6906   0.7751
  -2.000   0.1222   0.01992   0.01275  -0.0508   0.6776   0.7927
  -1.750   0.1445   0.02008   0.01283  -0.0487   0.6647   0.8100
  -1.500   0.1722   0.02028   0.01285  -0.0472   0.6540   0.8282
  -1.250   0.1960   0.02049   0.01300  -0.0453   0.6412   0.8457
  -1.000   0.2256   0.02074   0.01311  -0.0445   0.6298   0.8612
  -0.750   0.2596   0.02091   0.01311  -0.0449   0.6188   0.8731
  -0.500   0.2881   0.02106   0.01317  -0.0449   0.6075   0.8836
  -0.250   0.3190   0.02110   0.01300  -0.0453   0.5983   0.8932
   0.000   0.3423   0.02118   0.01305  -0.0447   0.5874   0.9031
   0.250   0.3862   0.02131   0.01292  -0.0476   0.5782   0.9088
   0.500   0.4115   0.02143   0.01305  -0.0476   0.5675   0.9174
   0.750   0.4545   0.02156   0.01296  -0.0506   0.5593   0.9227
   1.000   0.4813   0.02174   0.01316  -0.0509   0.5494   0.9307
   1.250   0.5237   0.02185   0.01307  -0.0539   0.5411   0.9357
   1.500   0.5513   0.02208   0.01332  -0.0546   0.5321   0.9436
   1.750   0.5931   0.02223   0.01334  -0.0576   0.5240   0.9488
   2.000   0.6234   0.02251   0.01356  -0.0588   0.5169   0.9562
   2.250   0.6631   0.02274   0.01378  -0.0617   0.5082   0.9619
   2.500   0.7000   0.02292   0.01375  -0.0639   0.5021   0.9690
   2.750   0.7353   0.02330   0.01425  -0.0663   0.4934   0.9754
   3.000   0.7726   0.02352   0.01440  -0.0688   0.4869   0.9826
   3.250   0.8133   0.02388   0.01467  -0.0720   0.4809   0.9894
   3.500   0.8488   0.02431   0.01521  -0.0747   0.4732   0.9972
   3.750   0.8741   0.02454   0.01537  -0.0750   0.4678   1.0000
   4.000   0.8897   0.02486   0.01558  -0.0736   0.4638   1.0000
   4.250   0.8835   0.02540   0.01631  -0.0689   0.4588   1.0000
   4.500   0.8816   0.02584   0.01680  -0.0647   0.4544   1.0000
   4.750   0.8961   0.02625   0.01714  -0.0629   0.4502   1.0000
   5.000   0.9207   0.02666   0.01738  -0.0626   0.4464   1.0000
   5.250   0.9278   0.02761   0.01846  -0.0597   0.4411   1.0000
   5.500   0.9429   0.02835   0.01925  -0.0580   0.4358   1.0000
   5.750   0.9663   0.02883   0.01968  -0.0575   0.4315   1.0000
   6.000   0.9949   0.02932   0.02005  -0.0578   0.4280   1.0000
   6.250   1.0015   0.03064   0.02155  -0.0550   0.4234   1.0000
   6.500   1.0124   0.03177   0.02281  -0.0530   0.4184   1.0000
   6.750   1.0347   0.03238   0.02341  -0.0523   0.4142   1.0000
   7.000   1.0649   0.03274   0.02367  -0.0528   0.4107   1.0000
   7.250   1.0754   0.03413   0.02518  -0.0508   0.4067   1.0000
   7.500   1.0709   0.03620   0.02749  -0.0472   0.4018   1.0000
   7.750   1.0833   0.03745   0.02882  -0.0456   0.3978   1.0000
   8.000   1.1111   0.03788   0.02921  -0.0457   0.3944   1.0000
   8.250   1.1482   0.03806   0.02929  -0.0470   0.3914   1.0000
   8.500   1.1015   0.04249   0.03414  -0.0393   0.3859   1.0000
   8.750   0.9390   0.05656   0.04859  -0.0274   0.3767   1.0000
   9.000   1.0341   0.05088   0.04282  -0.0293   0.3767   1.0000
   9.250   1.1211   0.04761   0.03945  -0.0338   0.3752   1.0000
  10.750   0.6168   0.12863   0.12115  -0.0449   0.3815   1.0000
  11.000   0.6379   0.13071   0.12325  -0.0450   0.3767   1.0000
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